Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Safran Aircraft Engines

Snecma

Hispano Suiza

Societe Nationale D'etude De Constudies De Mateurs D'aviation

Safran Power Units

Pierre Charles Mouton

Jean-Marie Brocard

Regis Michel Paul Deldalle

Michel A Desaulty

Jean-Louis Charbonnel

Bellal Waissi

Serge M Meunier

Xavier M Bardey

Sébastien Christophe Chalaud

Jean-Louis Muller

Jerome E Jolu

Chloe Avila

Marie-Lise Dardenne

Corinne Follonier

Anne Marie Cecile Barreau

Anne Marie Cécile Barreau

Régis Michel Paul Deldalle

Jacques Renvier

Sylvie Poutonnet

Arnaud Joudareff

A distributor valve comprising a second element configured to be displaced relative to a first element, so as to form an overall passage opening of variable fuel passage section corresponding to the intersection of a first passage opening and a second passage opening. The head portion of the second passage opening comprises a first inclination having a first average slope, the intermediate portion of the second passage opening comprises a second inclination having a second average slope strictly greater than said first average slope, and the foot portion of the second passage opening comprises a third inclination having a third average slope, strictly less than said second average slope.

Fuel distributor valve for fuel injector and method for operating such a distributor valve

A fluid supply system () for turbine engine, includes a high pressure volumetric pump (), a fluid metering device () and a control valve () configured to vary the flow rate of fluid in a bypass circuit () so as to regulate the pressure difference between an input and an output of the metering device (). The control valve () includes an obturator, the variable position of which is measured by a sensor (). An electronic regulation system () compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (). The flow rate of the high pressure pump () is commanded so that the measured position of the obturator adapts to the position set-point.

Fluid supply system for turbine engine, including an adjustable flow pump and a fluid metering device

The invention relates to a butterfly valve () for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (), a butterfly (), and a device () for controlling the angular position of the butterfly, the device () including a mobile actuation member () connected to the butterfly by a link (), the member () being subjected: to a first adjustable pressure force (F) applied by air from the compressor, the first force (F) returning the butterfly () to a closed position; and to a second mechanical force (F) returning the butterfly () to an open position, and coming from an aerodynamic torque (C) applied by the air to the butterfly (), of which the axis of rotation () is off-centre relative to the butterfly.

Butterfly valve for bleeding a compressor for an aircraft turbine engine

A fuel metering unit comprising a movable element including at least one fuel flow section opening upstream towards a fuel supply duct and opening downstream towards a utilization duct through a metering slot with a flared profile having a narrow flow section and a wide flow section, the movable element able to be moved with respect to a stationary element between a low flow rate position and a high flow rate position, the metering slot made in the stationary element or in the movable element and its obstruction obtained by covering the slot with a wall of the movable element or of the stationary element.

Fuel metering device protected against icing

The invention relates to a device () for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a duct () for circulating a flow of cold air (F), means () for injecting oil into the duct, and means () for extracting the oil mixed with the flow of cold air (F), located in the duct (), downstream from the injection means ().

Device for cooling oil for a turbine engine

A fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage section, the movable element being able to be moved with respect to a fixed element between a low flow rate position in which the metering slot is for a large part obstructed and a high flow rate position in which the metering slot is for a large part exposed, the metering slot being made in the fixed element or in the movable element and its obstruction being obtained by covering the slot with a wall of the movable element or of the fixed element.

Fuel meter protected from icing

A gas turbine engine incorporating a starter mounted on the gear box is disclosed. The gas turbine engine includes an AGB gear housing mechanically connected with an engine shaft for driving auxiliary machines and an air starter mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The oil enclosure of the starter is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Gas turbine engine comprising a starter in the auxiliary gear box

In an aircraft in which servocontrols are supplied with hydraulic fluid under pressure by a main pump driven by an engine of the aircraft and, in the event of loss of said engine power, by an emergency pump which is driven by a dynamic air pressure turbine deployed from the fuselage of the aircraft, a system is provided for assisting the restarting of said engine in the event of said aircraft suffering a total loss of engine power, wherein said main pump is of the reversible kind and means are provided for enabling surplus hydraulic power from the emergency pump to be supplied to the main pump whereby the latter acts as a hydraulic motor to increase the windmilling speed of the dead engine and thereby facilitate re-ignition thereof, even at a low aircraft speed.

System for restarting an aircraft engine in flight after loss of engine

A device for separating and filtering particles in a flow of contaminated fluid, the device including a casing having an inlet duct fitted with a cyclone separator designed to concentrate centrifugally particles in the inlet flow towards the periphery of the flow, a tubular element mounted in the casing with the upstream end of the element adjacent the inlet duct and having a diameter smaller than the inlet duct so that the substantially clean fluid from the cyclone separator flows into a central flow path within the tubular element and the contaminated fluid from the separator flows into a peripheral flow path between the tubular element and the casing, and a filter mounted in the casing adjacent an outlet duct so that the clean fluid in the central flow path passes through a central passage of the filter to the outlet duct and the contaminated fluid in the peripheral flow path is filtered by the filter to form a filtered flow which mixes with the clean fluid in the central passage whereby the fluid flow rate in the outlet duct is the same as in the inlet duct.

Device for separating and filtering particles in a flow of fluid

A method and apparatus for detecting a fouled fluid filter are disclosed in which the fluid pressure at the outlet of the fluid filter is corrected by a correction pressure to determine a corrected pressure drop. Such a corrected pressure drop has a mathematical function which passes through a maximum magnitude before the fluid flowing through the fluid filter reaches a maximum value. The corrected pressure drop is monitored during the operation of the fluid filter and when the corrected pressure drop reaches a predetermined threshold value, before the engine with which the fluid filter is associated reaches its maximum power, an alarm will be actuated.

Method and apparatus for detecting a fouled fluid filter

An anti-icing system to prevent the formation of ice on, or to remove ice from selected portions of a gas turbine engine is disclosed that is not directly dependent upon the mode or speed of operation of the gas turbine engine. The system has a heat exchanger into which flows a tapped portion of air from the compressor and fuel from the engines fuel supply system. The fuel supply system includes a fuel return circuit which connects the fuel pump outlet to the fuel pump inlet so as to return or recycle fuel to the fuel pump inlet when the engine demand for fuel is low, such as under lower power operating conditions. This recycling of the fuel raises the temperature of the fuel such that, in the heat exchanger, heat is transferred to the tapped portion of the air from the compressor thereby raising the temperature of such tapped air such that it may be directed onto selected portions of the gas turbine engine to either prevent formation of ice, or to remove ice from these portions. Under high speed engine operating conditions, such as full power, the engines demand for fuel is greater resulting in less fuel recycling and lower fuel temperature. Under these conditions, the temperature of the fuel is lower than that of the air tapped from the compressor resulting in heat transfer from the tapped air to the fuel. This lowers the temperature of the tapped air so as to prevent damage to the forward engine bearings onto which the air may be directed to prevent ice formation.

Anti-icing system for a gas turbine engine

A gas turbine engine is disclosed having an air compressor and a generally annular combustion chamber, with a generally annular diffuser located between the compressor and the combustion chamber so as to direct air exiting from the compressor toward the combustion chamber. The diffuser has inner and outer walls and defines an exit which is located adjacent to an opening in an upstream wall portion of the combustion forming a dome cowl. The dome cowl divides the air emanating from the diffuser exit into a primary air stream passing through the opening and one or more secondary air streams which pass between the walls defining the combustion chamber and the walls of a casing enclosing the combustion chamber assembly. A guide is associated with the diffuser for directing water in the air passing through the diffuser away from the opening such that it will not pass directly into the combustion chamber. Guide vanes may be located on an external surface of the dome cowl so as to direct the water in the secondary air-flow such that it does not enter openings defined by the outer combustion chamber wall, thereby preventing the water from entering the combustion chamber.

Gas turbine engine with improved water ingestion prevention

A system is disclosed for detecting a malfunction in a fuel/lubricating oil heat exchanger which includes a pressure differential generator located in the pressure balancing conduit connecting the lubricating oil reservoir with the lubricating enclosure. The pressure differential generator may be a cavitation venturi tube having a throat which, under normal conditions, allows sub-sonic fluid flow which enables the air in the lubricating enclosure to freely communicate with the interior of the oil reservoir and vice versa. When fuel is mixed with the lubricating oil, due to a malfunction in the fuel/oil heat exchanger, the fuel enters the lubricating oil reservoir causing the fluid level within the reservoir to rise and overflow. The cavitation venturi tube is then supplied with a comparatively hot mixture of fuel and oil having a vapor pressure approximately equal to the reference pressure within the lubricating enclosure. Under these conditions, vaporization takes place at the throat of the venturi tube which effectively blocks any fluid flow through the venturi. As a result, the pressure within the oil reservoir increases.

Pressure system for detecting malfunctions of a fuel/oil heat exchanger

An anti-flameout safety system for a gas turbine engine is disclosed which prevents engine flameout in the event of ingestion of hail and/or water through the engine intake. The anti-flameout safety system has a detector to detect the water concentration in the engine which generates a signal when the water concentration is at or above a predetermined level and an engine control means which is associated with the detector such that, when the detector generates the signal, the engine control means automatically increases the engine power output.

Anti-flameout safety system for a gas turbine engine

A sealed transmission assembly coupling a first rotary shaft mounted in a first casing to a second rotary shaft substantially aligned with the first shaft and mounted in a second casing fixed to the first casing is disclosed which enables replacement of leaky seals or part of the transmission chain to be effected quickly and without disconnecting the second casing from the first casing. In this assembly the first shaft is tubular, the second casing has a tubular protrusion which extends through the first casing inside the first shaft and projects into a chamber defined by a cover which is removably secured to the first casing on the opposite side from the second casing, the second shaft has an extension projecting through the tubular protrusion, a removable driving member connects the end of the extension to the first shaft for rotation therewith, and removable sealing means are disposed between the driving member and the end of the tubular protrusion projecting into the chamber, the arrangement being such that the driving member and the sealing means can be disassembled, after removal of the cover, without disconnecting the second casing.

Growing community of inventors

Grigny, France

Pierre Charles Mouton